Aeroplane.



F. McCARROLL.

AEROPLANE.

APPHCATION man NOV. s. 19H.

PatentedSept. 7, 1915.

2 SHEETS-SHEET I WITNESSES:

F. McCARROLL;

AEROPLANE.

APPLICATION FILED NOV- 3, 1911.

Patented Sept. 7, 1915.

2 SHEETSSHEET 2.

WITNESSES:

3 an snares Partner easier.-

7 FRANK McC'ARROLL, or DALLAS, TEXAS.

annornann.

Application filed November 3, 1911.

, the forward and rearward lateral edges of the fixed section. The particular object of such an arrangement is to vary the curvature of the plane from front to rear and i by this means the plane may be so adjusted as to 'reduce the head resistance to a minimum.

Another object is to provide suitable means for manipulating theadjustable sec tions whereby the movable sections of a plane may be simultaneously swung upward or downward; or by which the adjustable sections of a pair of planes may be swung in opposed relation to retain the lateral equilibrium of an aeroplane.

It is obvious that the running gear of an aeroplane offers more or less resistance to the forward movement of the same and this is termed head resistance.

One of the objects of this invention is to swing the running gear up into the frame of theaeroplane whereby it will odor less resistance to the forward movement of the aeroplane than where said running gear hangs pendant from the frame.

A still further object of the invention is to provide a machine that will be strong, durable and efficient and comparatively simple to construct, also one in which the several parts will not be likely to get out of working order.

With the above and other objects in view the invention has relation to certain novel features of construction and operation, an example of which is described in the following specification and illustrated in the accompanying drawings, wherein:

Figure 1 is a plan View of the forward portion of an aeroplane equipped with this invention, Fig. 2- is a side elevation of the same aeroplane, Fig. 3 is a transverse vertical sectional View on the line ss of Fig. 2, Fig. 4c is a transverse sectional view of one Specification of Letters Patent.

Patented dept. *2, 1915.

Serial 1\To.-658,328.

of the planes, Fig. 5 is an enlarged detail transverse section through one of the planes, Fig. 6 is a detail of the adjusting means for the planes, Fig. 7 is an elevation of the parts illustrated in Fig. 6, but shown at right angles thereto, and Fig. 8 is a horizon- I tal cross sectional view on the line -00 of Fig. 6.

In the drawings the numeral 1 designates the frame of a monoplane and it will be noted by observing Fig. 3 that this frame is triangular in cross section. It has been customary to make these frames rectangular in cross section and it is believed the shape of frame herein shown will offer less resistance to the forward movement of the machine than those now commonly in use. At the rear of the frame a suitable rudder 2 and rear planes 3 are provided. A skid 4: depends from the rear end of the frame for supporting the same when on the ground. At the forward end of the frame a suitable propeller 5 is mounted and connected to an engine 6 also carried in the forward portion of the frame.

At each side of the frame near the f0rward end wings 7 are secured and extend laterally on each side of said frame in the usual manner. As the construction of one wing is substantially the same as the other are secured to longitudinal T-beams 14 interposed between the upper and lower ribs. On these ribs fabric 15 is fastened so that the sections will have upper and under surfaces. The said sections are constructed separately but so shaped that when assembled a complete and properly curved plane will be produced. The intermediate sect-ion 9 is fixed to the frame 1 and is suitably supported against movement. The other sections are hinged to the fixed section and are adjustable. The hinged joint between the sectlons may be made in any approved manner and in Fig. 5 I have shown flanged hinged members 16 connected together and secured to the adjacent T-beams'of the sections. For covering the joints between the sections flaps 1] are provided and directed rearward so as to cover the spaces at the joints and lie in close contact with the fabric coverings when the machine is in operation.

A tubular rock shaft 18 extends longitudinally through the section 9 and is supported in bearings 19 secured to the inner sides of the ribs 11 and 12 between the same. On this shaft cross arms 20 are centrally secured so as to project on each side of said shaft. The free ends of the arms terminate in close proximity to the ribs and are provided with suitable means for fastening the inner ends of flexible connections 21 and 22 respectively thereto. The connections 21 extend forward through the lf-beam and are fastened'to the rear I-beam of the section 8; while the connections 22 are crossed and pass through "the T-beam and fastened to the forward I-beam of the section 10.

, By the above arrangement the sections 8 and 10 are held in position and when the rock shaft is swung it is obvious that said sections 8 and 10 will be moved in unison either up or down. It is to be noted that the means for controlling, operating and supporting the adjustable sections is entirely concealed and contained in the wing between its fabric coverings and is thus protected and oflers no resistance to the forward movement of the wing during flight.

It has been established that for making a high rate of speed a comparatively flat wing or one having but a slight curvature from front to rear is most efficient-x Where altitude flying is desired a wing having considerable curvature has been found best. It is customary to have two or more sets of wings for an aeroplane and these sets have different curvatures. A set of wings is secured to the frame in accordance with the character of. flying to be done. This arrangement not only adds to the. expense but is inconvenient and requires considerable time to make the change. Furthermore the curvature cannot be changed during flight.

It is apparent that by swinging the rock shaft 18 of the wing herein described the sections 8 and 10 are adjusted. When said sections are swung downward the curvature of the wing from front to rear is increased but if said sections are swung upward the curvature is diminished. This adjustment may be accomplished immediately and during flight and. the aviator hasat his commandany desired curvature. As shown in Figs. 1 and 3 two of said wings are secured to the frame 1. The rock shafts 18 are terminated adjacent each other and at one side of the frame. The said ends of the shaft are received in sockets 23 extending in opposed relation from a vertical sleeve 24 as shown in Fig. 6. A lever 25 is loosely mounted in the sleeve but is confined against longitudinal movement by collars 26 and 27 fixed on said lever and bearing against the ends of the sleeve. On each rock shaft a depending arm 28 is fastened adjacent the socket 23 thereof. A cross lever 29 is censections8 and 10 of one plane are swung upward and the forward and rearward sections of the other plane swung down any tendency of the aeroplane to lose its lateral equilibrium would be checked, as the sections swung down would oppose the sections which are swung upward. For eflecting this adjustment lever arm 31 extends laterally from the lever 25 and is provided with a spring pressed latch 32 engaging a toothed collar 33 mounted on the sleeve 24. When the lever arm is swung it rotates the lever 25 which rotates the cross lever 29.

When the cross lever is rotated the arms- 28 will be swung in opposite directions thus rocking the shafts 18 in opposite directions as will be apparent.

As hereinbefore stated the object of this invention is to diminish the head resist ance and this is partially accomplished by the triangular frame and the provision whereby the curvature of each plane may be reduced. By reducing the curvature of the planes it is evident that they. will present less surface when-moved forward and thus offering less resistance a higher rate of speed may be attained. The curvature of the planes may be increased or decreased for several reasons and under different 'conditions. The adjustable plane herein described has a particular co-action with another invention involving the principles of flight and for which I shall later file apphcation for Letters Patent.

A bird in flying never permits its feet to hang or depend from its body but has them closely gathered into its plumage for' the reason that the feet and legs would offer resistance to the flight if they depended from the body. The running gear of an aeroplane bears the same relation to the frame as a birds feet do to its body. As shown in the drawings I have provided a running gear which is hinged and arranged to be swung up against the frame thus obviating the resistance usually oflered by the depending gear. From the under center portion of the frame 1 a tubular support 3 1 inclines downward and forward and terminates in a curved shoe 35 extending under the propeller 5. This support is held in position by a brace 36 also extending from the frame. The shoe protects the propeller in case the machine strikes the ground with more force than will be ofi'set by the shock absorbers of the running gear. To each side of the frame wheel supports 37 are hinged. These supports are of the ordinary construction and are provided with the usual shock absorbers. From each support a spreader bar 38 extends forward to a block or carriage 39 slidable on the support 34. Each bar 38 is pivoted at each end. Also from each wheel support another spreader bar 40-pivoted thereto extends rearward and upward and has pivotal connection with the frame An endless chain 41 passes over pulleys 42 mounted on the support 34, one run of the chain traveling through said tubular support. The chain is fastened to the block 39 and suitable means is provided on the frame for imparting motion to one of the pulleys 42 and the chain 41. As shown in Fig. 2 the running gear is pendant and in position to support the machine on the ground, the block 39 being at the lower end of the support 34. After the machine'leaves the ground in ascending the aviator imparts motion to the chain 41 which slides the block arms or supports 37 are at widely separated points at opposite sides of the frame. The

sliding bearing connection of the arms 40 with the lower member 1 of the frame are made in the same manner as the connections of the arms 38 with the brace arm 34, a carrier 40 being movable alongthe member 1, and the arms 40 extending inwardly and rearwardly from the points of connection with the wheel supports to said'carrier, so that as the supports 37 swing rearwardly and upwardly they readily carry by. the arms 40.

I What I claim, is: a

-1. A running gear for aeroplanes, comprising in combination with a frame-work, an lncllned slide-member carried by said and pivotal connections between said wheelsupports and said slidable carriage, whereby said wheel-supports are swung into said frame-work when said carriage is moved upwardly.

3. A running gear for aeroplanes, comprising in combination with a frame-work, wheel carrying supports pivotally carried by said frame, a carriage mounted for movement upwardly into said frame, a rigid slide-member for guiding the movement of said carriage, and means 'operatively connecting said wheel carrying supports and said carriage whereby said supports are carried upwardly into said frame, when said carriage is actuated upwardly.

'. 4. A running gear for aeroplanes, comprising in combination, with a frame-work, wheel carrying supports pivotally mounted on said frame, a rigid slide-member for guiding the movement of said carriage, connecting rods pivotally joining said wheel supports and said carriage for throwing said supports upwardly into said frame when said carriage moves upwardly, the operation being such that said wheel-supports are also drawninwardlv against said frame, and means for operating said carriage. I

In testimony whereof I have signed my name to this specification inthe presence of two subscrlbing witnesses.

FRANK MGGARROLL.

Witnesses: v

MAME MGCARROLL, JACK A. ScHLEY. 

